WO2008023070A1 - Compressor housing - Google Patents

Compressor housing Download PDF

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Publication number
WO2008023070A1
WO2008023070A1 PCT/EP2007/058851 EP2007058851W WO2008023070A1 WO 2008023070 A1 WO2008023070 A1 WO 2008023070A1 EP 2007058851 W EP2007058851 W EP 2007058851W WO 2008023070 A1 WO2008023070 A1 WO 2008023070A1
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WO
WIPO (PCT)
Prior art keywords
compressor
stabilizer
housing
groove
stabilizer space
Prior art date
Application number
PCT/EP2007/058851
Other languages
German (de)
French (fr)
Inventor
Fabian SCHÖNBÄCHLER
Matthias Schleer
Marc Andrea Camastral
Markus Städeli
Peter Neuenschwander
Original Assignee
Abb Turbo Systems Ag
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=38814521&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=WO2008023070(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Abb Turbo Systems Ag filed Critical Abb Turbo Systems Ag
Priority to JP2009525082A priority Critical patent/JP5248501B2/en
Priority to CN2007800312088A priority patent/CN101506488B/en
Priority to EP07802892.5A priority patent/EP2054595B1/en
Publication of WO2008023070A1 publication Critical patent/WO2008023070A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B33/00—Engines characterised by provision of pumps for charging or scavenging
    • F02B33/32—Engines with pumps other than of reciprocating-piston type
    • F02B33/34—Engines with pumps other than of reciprocating-piston type with rotary pumps
    • F02B33/40—Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines. It relates to a compressor of such an exhaust gas turbocharger.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines, in particular reciprocating engines.
  • an exhaust gas turbocharger usually has a centrifugal compressor and a radial or axial turbine.
  • bypass mass flows result, which allow a shift towards smaller or larger volume flows in the region of the surge line, ie in the area of minimum volumetric flow promotion and in the area of the intake limit, ie in the region of maximum volumetric flow promotion with identical machines without bypass.
  • the stabilizer space is formed as an elongate, narrow channel.
  • the object of the invention is to improve a compressor by a new structural design of the stabilizer space.
  • the inner compressor housing that is, the part inside the outer spiral housing is formed in one piece. This is the flow channel from the axial
  • Compressor wheel limiting housing part is formed as a component. The deflected from the axial to the radial direction flow channel is on this
  • the stabilizer space In the interior of the one-piece housing of the stabilizer space is arranged, which expands according to the invention via a variable in the axial direction, large radial height. This results in an optimal turbulence of the recirculation flow through the stabilizer space.
  • the stabilizer space is opened via two openings to the flow channel. Upstream of the compressor wheel is arranged a radial inlet opening and downstream of the leading edge of the compressor wheel and in the overlap area to the inlet of a radial contour groove.
  • the arranged between the circumferential openings ring land forms a part of the Strömungsungsanalwand and is connected via a plurality of retaining ribs with the inner compressor housing.
  • the holding ribs can be provided with vibration-reducing measures.
  • the holding ribs can be arranged obliquely with respect to the radial direction. Or they can be profiled and / or arranged twisted around their own axis. Several holding ribs can be arranged obliquely opposite one another in order to increase the rigidity and thus to achieve a high natural frequency of the intake geometry.
  • this variant allows for different compressor stages implement a variable spiral cross-section.
  • thermal insulation may be applied to the housing wall which separates the stabilizer space from the flow channel. Thereby, the heat input can be reduced to the air circulating in the stabilizer room.
  • sound-absorbing means can be arranged in the stabilizer room without additional structural measures.
  • Fig. 1 shows a compressor housing with an integrated insert wall
  • Fig. 2 shows the opposite inclined position of the holding ribs against the center without misalignment of the stiffening ribs.
  • Fig. 1 shows a section of an inventively designed radial compressor, as it is used for example in exhaust gas turbochargers.
  • the outer compressor housing 20 and the inner compressor housing 10 are divided in the region of the spiral housing.
  • the outer compressor housing 20 is fixed to the right of the bearing housing, not shown, on the back of the compressor wheel 40.
  • the inner compressor housing 10 comprises a part of the spiral and the housing parts forming the flow channel upstream of the spiral, the insert wall 12 and, upstream of the compressor wheel 40, the compressor inlet.
  • the stabilizer chamber 60 is opened via two openings to the flow channel.
  • a radial inlet groove 14 is arranged, which is bounded by a housing part in the intake, for example, a housing part of a muffler or intake, and the compressor inlet.
  • the cross section of the stabilizer space 60 is due the spiral is not constant along the circumference.
  • the average radial height of the stabilizer space is at least approximately two-thirds of the axial distance between inlet groove 14 and contour groove 13. Thanks to the uneven and large radial height of the stabilizer space, an optimal turbulence of the recirculation flow through the stabilizer chamber results, which has a positive effect on the generated Noise affects.
  • the not constant along the circumference cross-sectional profile provides additional acoustic improvement.
  • the inner compressor housing 10 with axially extending
  • Stiffening ribs 15 are selectively reinforced. As a result, any loads can be counteracted, which due to the distribution of the spiral geometry to two
  • Housing parts in the inner compressor housing may arise.
  • Stiffening ribs can be selected according to the expected load.
  • the stiffening ribs may optionally be formed twisted around the loader axis.
  • the stiffening ribs may optionally be arranged obliquely to the radial direction.
  • the edge of the stiffening ribs can optionally be rotationally symmetrical.
  • the stiffening ribs may optionally have a conical shape.
  • the separation of the wall insert geometry in the compressor inlet through the contour groove requires a separate attachment of the annular web 11.
  • This attachment is realized by radially outwardly directed retaining ribs 16.
  • vibration-reducing measures can be implemented.
  • the retaining ribs can optionally be formed rotated about its axis.
  • the holding ribs can optionally be inclined against the radial direction.
  • the retaining ribs may have different deviations from the radial direction.
  • the holding ribs can also be arranged skewed in opposite directions.
  • the holding ribs can optionally be equipped with a round, conical or elliptical profile or with a flow profile.
  • the design of the retaining ribs allows the installation of optional sound-absorbing measures in the stabilizer space with little additional constructive auxiliary measures.
  • the overall very soft structure of the integrated inner compressor housing has a positive effect on the behavior in the event of bursting of the compressor wheel.
  • the long housing parts can be easily deformed and absorb a large part of the energy stored in the compressor wheel.
  • guide vanes 25 of the diffuser are optionally arranged on the integrated housing wall 10.
  • the profiles are provided as a ring during casting of the integrated inner compressor housing and milled to the required mass during finishing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

The object of the invention is to provide a compressor stage for more stringent efficiency requirements. To this end, the design of the diffusor/spiral section has been modified. In detail, a high stabilizer area (60) and integration of the insert wall and of the compressor housing are provided.

Description

Verd ichtergehäuse Compressor housing
B E S C H R E I B U N GDESCRIPTION
Technisches GebietTechnical area
Die Erfindung bezieht sich auf das Gebiet der Abgasturbolader für aufgeladene Brennkraftmaschinen. Sie betrifft einen Verdichter eines solchen Abgasturboladers.The invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines. It relates to a compressor of such an exhaust gas turbocharger.
Stand der TechnikState of the art
Abgasturbolader werden zur Leistungssteigerung von Brennkraftmaschinen, insbesondere Hubkolbenmotoren, eingesetzt. Dabei besitzt ein Abgasturbolader üblicherweise einen Radialverdichter und eine Radial- oder Axialturbine.Exhaust gas turbochargers are used to increase the performance of internal combustion engines, in particular reciprocating engines. In this case, an exhaust gas turbocharger usually has a centrifugal compressor and a radial or axial turbine.
Als Kennlinien-Stabilisierungs-Massnahme wird dabei über der Radkontur des Verdichterrades etwa im ersten Viertel der Radlänge, parallel zum Ansaugkanal, ein Bypass in Form eines Ringspaltes innerhalb des Verdichtergehäuses vorgesehen, wobei dieser Bypass aus einer stromauf zum Verdichterrad liegenden radialen Eintrittsnut, einer stromab zur Eintrittskante des Verdichterrades liegenden radialen Konturnut und einem diese beiden Nuten verbindenden Stabilisatorraum gebildet ist.As a characteristic stabilization measure is thereby provided over the wheel contour of the compressor wheel approximately in the first quarter of the wheel length, parallel to the intake passage, a bypass in the form of an annular gap within the compressor housing, said bypass of an upstream of the compressor wheel radial inlet groove, downstream to The leading edge of the compressor wheel lying radial contour groove and a connecting these two grooves stabilizer space is formed.
Durch den parallel zum Ansaugkanal und damit zum eigentlichen Radeintritt liegenden Stabilisatorraum ergeben sich Bypassmassenströme, die im Bereich der Pumpgrenze, also im Bereich minimaler Volumenstromförderung und im Bereich der Schluckgrenze, also im Bereich maximaler Volumenstromförderung eine Verschiebung in Richtung kleinerer bzw. grosserer Volumenströme ermöglichen, verglichen mit bauartgleichen Maschinen ohne Bypass.Due to the stabilizer space lying parallel to the intake passage and thus to the actual wheel entry, bypass mass flows result, which allow a shift towards smaller or larger volume flows in the region of the surge line, ie in the area of minimum volumetric flow promotion and in the area of the intake limit, ie in the region of maximum volumetric flow promotion with identical machines without bypass.
Bei herkömmlichen Verdichtern ist der Stabilisatorraum als ein länglicher, schmaler Kanal ausgebildet. Die dadurch insbesondere bei grossen Verdichtern benötigten zusätzlichen Gehäusewandteile führen zu sehr grossen komplexen Gussformen mit vielen Kernen. Kurze Darstellung der ErfindungIn conventional compressors, the stabilizer space is formed as an elongate, narrow channel. The additional housing wall parts required thereby, in particular for large compressors lead to very large complex molds with many cores. Brief description of the invention
Aufgabe der Erfindung ist, einen Verdichter durch eine neue konstruktive Ausgestaltung des Stabilisatorraums zu verbessern.The object of the invention is to improve a compressor by a new structural design of the stabilizer space.
Erfindungsgemäss wird das innere Verdichtergehäuse, also der Teil innerhalb des äusseren Spiralgehäuses einteilig ausgebildet. Das den Ström ungskanal vom axialenAccording to the invention, the inner compressor housing, that is, the part inside the outer spiral housing is formed in one piece. This is the flow channel from the axial
Einlauf im Bereich des axialen Ansaugkanals bis in den Diffusor stromabwärts desInlet in the region of the axial intake channel to the diffuser downstream of the
Verdichterrades begrenzende Gehäuseteil ist als ein Bauteil ausgebildet. Der von der axialen in die radiale Richtung umgelenkte Strömungskanal ist auf der diesemCompressor wheel limiting housing part is formed as a component. The deflected from the axial to the radial direction flow channel is on this
Gehäuseteil gegenüberliegenden Seite durch die Nabe des Verdichterrades sowie weiter stromab durch eine Diffusorrückwand begrenzt.Housing part opposite side limited by the hub of the compressor wheel and further downstream through a diffuser rear wall.
Im Innern des einteilig ausgebildeten Gehäuses ist der Stabilisatorraum angeordnet, welcher sich erfindungsgemäss über eine in axialer Richtung variable, grosse radiale Höhe ausdehnt. Dadurch ergibt sich eine optimale Verwirbelung der Rezirkulationsströmung durch den Stabilisatorraum. Der Stabilisatorraum ist über zwei Öffnungen zum Strömungskanal hin geöffnet. Stromauf zum Verdichterrad ist einer radiale Eintrittsöffnung angeordnet und stromab zur Eintrittskante des Verdichterrades und im Überdeckungsbereich zu dessen Einlauf eine radiale Konturnut. Der zwischen den umlaufenden Öffnungen angeordnete Ringsteg bildet einen Teil der Strömungsanalwand und ist über mehrere Halterippen mit dem inneren Verdichtergehäuse verbunden.In the interior of the one-piece housing of the stabilizer space is arranged, which expands according to the invention via a variable in the axial direction, large radial height. This results in an optimal turbulence of the recirculation flow through the stabilizer space. The stabilizer space is opened via two openings to the flow channel. Upstream of the compressor wheel is arranged a radial inlet opening and downstream of the leading edge of the compressor wheel and in the overlap area to the inlet of a radial contour groove. The arranged between the circumferential openings ring land forms a part of the Strömungsungsanalwand and is connected via a plurality of retaining ribs with the inner compressor housing.
Optional können die Halterippen mit Schwingungsreduzierenden Massnahmen versehen sein. Beispielsweise können die Halterippen bezüglich der radialen Richtung schräg angeordnet sein. Oder sie können profiliert und/ oder um die eigene Achse verdreht angeordnet sein. Mehrere Halterippen können gegenläufige schief angeordnet sein, um die Steifigkeit zu erhöhen und somit eine hohe Eigenfrequenz der Einlaufgeometrie zu erzielen.Optionally, the holding ribs can be provided with vibration-reducing measures. For example, the holding ribs can be arranged obliquely with respect to the radial direction. Or they can be profiled and / or arranged twisted around their own axis. Several holding ribs can be arranged obliquely opposite one another in order to increase the rigidity and thus to achieve a high natural frequency of the intake geometry.
Mit dieser Variante wird eine markante Kostensenkung für das fertige Bauteil erwartet. Weiterhin erlaubt diese Variante für verschiedene Verdichterstufen einen variablen Spiralquerschnitt umzusetzen. Optional können auf der Gehäusewand, welche den Stabilisatorraum vom Strömungskanal trennt, thermische Isolationen aufgebracht sein. Dadurch kann der Wärmeeintrag auf die im Stabilisatorraum zirkulierende Luft verringert werden. Optional können im Stabilisatorraum ohne zusätzliche konstruktive Massnahmen schalldämmende Mittel angeordnet sein.With this variant, a significant cost reduction for the finished component is expected. Furthermore, this variant allows for different compressor stages implement a variable spiral cross-section. Optionally, thermal insulation may be applied to the housing wall which separates the stabilizer space from the flow channel. Thereby, the heat input can be reduced to the air circulating in the stabilizer room. Optionally sound-absorbing means can be arranged in the stabilizer room without additional structural measures.
Kurze Beschreibung der ZeichnungenBrief description of the drawings
Im folgenden ist anhand der Figuren die erfindungsgemässe Vorrichtung schematisch dargestellt und näher erläutert.In the following, the device according to the invention is shown schematically and explained in more detail with reference to the figures.
In allen Figuren sind gleichwirkende Elemente mit gleichen Bezugszeichen versehen: Fig. 1 zeigt ein Verdichtergehäuse mit einer integrierten Einsatzwand, undIn all figures, the same elements are provided with the same reference numerals: Fig. 1 shows a compressor housing with an integrated insert wall, and
Fig. 2 zeigt die gegenläufige Schiefstellung der Halterippen gegen das Zentrum ohne Schiefstellung der Versteifungsrippen.Fig. 2 shows the opposite inclined position of the holding ribs against the center without misalignment of the stiffening ribs.
Weg zur Ausführung der ErfindungWay to carry out the invention
Fig. 1 zeigt einen Ausschnitt eines erfindungsgemäss ausgebildeten Radialverdichters, wie er etwa in Abgasturboladern eingesetzt wird. Das äussere Verdichtergehäuse 20 und das innere Verdichtergehäuse 10 sind im Bereich des Spiralgehäuses geteilt. Das äussere Verdichtergehäuse 20 wird rechts am nicht dargestellten Lagergehäuse, auf der Rückseite des Verdichterrades 40, befestigt. Das innere Verdichtergehäuse 10 umfasst einen Teil der Spirale sowie die den Strömungskanal stromauf der Spirale bildenden Gehäuseteile, die Einsatzwand 12 sowie stromauf des Verdichterrades 40 den Verdichtereinlauf.Fig. 1 shows a section of an inventively designed radial compressor, as it is used for example in exhaust gas turbochargers. The outer compressor housing 20 and the inner compressor housing 10 are divided in the region of the spiral housing. The outer compressor housing 20 is fixed to the right of the bearing housing, not shown, on the back of the compressor wheel 40. The inner compressor housing 10 comprises a part of the spiral and the housing parts forming the flow channel upstream of the spiral, the insert wall 12 and, upstream of the compressor wheel 40, the compressor inlet.
Im Innern des einteilig ausgebildeten inneren Verdichtergehäuses 10 ist der Stabilisatorraum 60 angeordnet, welcher sich erfindungsgemäss über eine in axialerIn the interior of the integrally formed inner compressor housing 10 of the stabilizer space 60 is arranged, which according to the invention via an axial
Richtung und in Umfangshchtung unregelmässig verlaufende, grosse radiale Höhe ausdehnt. Der Stabilisatorraum 60 ist über zwei Öffnungen zum Strömungskanal hin geöffnet. Stromauf des Verdichterrades ist eine radiale Eintrittsnut 14 angeordnet, welche durch ein Gehäuseteil im Ansaugbereich, beispielsweise einem Gehäuseteil eines Schalldämpfers oder Ansaugstutzens, sowie den Verdichtereinlauf begrenzt ist.Direction and in the circumferential direction irregularly extending, large radial height expands. The stabilizer chamber 60 is opened via two openings to the flow channel. Upstream of the compressor wheel, a radial inlet groove 14 is arranged, which is bounded by a housing part in the intake, for example, a housing part of a muffler or intake, and the compressor inlet.
Stromab der Eintrittskante des Verdichterrades 40 und im Überdeckungsbereich zu dessen Einlauf ist eine radiale Konturnut 13 angeordnet. Der zwischen den umlaufenden Nuten angeordnete Ringsteg 11 bildet im Bereich des Verdichtereinlaufs die Strömungskanalwand und ist über mehrere Halterippen 16 mit dem inneren Verdichtergehäuse verbunden. Der Querschnitt des Stabilisatorraums 60 ist aufgrund der Spirale entlang dem Umfang nicht konstant. Die durchschnittliche radiale Höhe des Stabilisatorraums beträgt erfindungsgemäss jedoch mindestens rund zwei Drittel des axialen Abstandes von Eintrittsnut 14 und Konturnut 13. Dank der ungleichmässig verlaufenden und grossen radialen Höhe des Stabilisatorraums ergibt sich eine optimale Verwirbelung der Rezirkulationsströmung durch den Stabilisatorraum, was sich positiv auf den erzeugten Lärm auswirkt. Zudem sorgt der entlang dem Umfang nicht konstante Querschnittsverlauf für eine zusätzliche akustische Verbesserung.Downstream of the leading edge of the compressor wheel 40 and in the overlap region to the inlet of a radial contour groove 13 is arranged. The arranged between the circumferential grooves ring land 11 forms the flow channel wall in the region of the compressor inlet and is connected via a plurality of retaining ribs 16 with the inner compressor housing. The cross section of the stabilizer space 60 is due the spiral is not constant along the circumference. However, according to the invention, the average radial height of the stabilizer space is at least approximately two-thirds of the axial distance between inlet groove 14 and contour groove 13. Thanks to the uneven and large radial height of the stabilizer space, an optimal turbulence of the recirculation flow through the stabilizer chamber results, which has a positive effect on the generated Noise affects. In addition, the not constant along the circumference cross-sectional profile provides additional acoustic improvement.
Optional kann das innere Verdichtergehäuse 10 mit axial verlaufendenOptionally, the inner compressor housing 10 with axially extending
Versteifungsrippen 15 gezielt verstärkt werden. Dadurch kann allfälligen Belastungen entgegengewirkt werden, welche aufgrund der Aufteilung der Spiralgeometrie auf zweiStiffening ribs 15 are selectively reinforced. As a result, any loads can be counteracted, which due to the distribution of the spiral geometry to two
Gehäuseteile im inneren Verdichtergehäuse entstehen können. Die Anzahl derHousing parts in the inner compressor housing may arise. The number of
Versteifungsrippen kann der zu erwartenden Belastung entsprechend gewählt werden.Stiffening ribs can be selected according to the expected load.
Die Versteifungsrippen können optional um die Lader-Achse verdreht ausgebildet sein.The stiffening ribs may optionally be formed twisted around the loader axis.
Die Versteifungsrippen können optional schräg zur radialen Richtung angeordnet sein. Die Kante der Versteifungsrippen kann optional rotationssymmetrisch ausgebildet sein.The stiffening ribs may optionally be arranged obliquely to the radial direction. The edge of the stiffening ribs can optionally be rotationally symmetrical.
Die Versteifungsrippen können optional eine konische Form aufweisen.The stiffening ribs may optionally have a conical shape.
Die Durchtrennung der Einsatzwandgeometrie im Verdichtereinlauf durch die Konturnut erfordert eine separate Befestigung des Ringstegs 11. Diese Befestigung wird durch radial nach aussen gerichtete Halterippen 16 realisiert. Optional können Schwingungsreduzierende Massnahmen verwirklicht sein. So können die Halterippen optional um ihre Achse verdreht ausgebildet sein. Die Halterippen können optional gegen die radiale Richtung schräg gestellt sein. Dabei können die Halterippen unterschiedliche Abweichungen zur radialen Richtung aufweisen. Insbesondere können die Halterippen auch gegenläufig schief gestellt angeordnet sein. Durch die in Fig. 2 dargestellte Schiefstellung der Halterippen 16 gegen die radiale Richtung, insbesondere durch eine ungleiche bzw. eine gegenläufige Schiefstellung kann das Schwingungsverhalten gezielt beeinflusst werden.The separation of the wall insert geometry in the compressor inlet through the contour groove requires a separate attachment of the annular web 11. This attachment is realized by radially outwardly directed retaining ribs 16. Optionally, vibration-reducing measures can be implemented. Thus, the retaining ribs can optionally be formed rotated about its axis. The holding ribs can optionally be inclined against the radial direction. The retaining ribs may have different deviations from the radial direction. In particular, the holding ribs can also be arranged skewed in opposite directions. By the misalignment of the holding ribs 16 shown in FIG. 2 against the radial direction, in particular by an unequal or an opposite skew, the vibration behavior can be selectively influenced.
Die Halterippen können optional mit einem runden, konischen oder elliptischen Profil oder mit einem Strömungsprofil ausgestattet sein. Die Ausgestaltung der Halterippen erlaubt den Einbau optionaler schalldämmender Massnahmen in den Stabilisatorraum mit geringen zusätzlichen konstruktiven Hilfsmassnahmen. Die insgesamt sehr weiche Struktur des integrierten inneren Verdichtergehäuses hat eine positive Auswirkung auf das Verhalten im Berstfall des Verdichterrades. Die langen Gehäuseteile lassen sich gut deformieren und absorbieren einen grossen Teil der im Verdichterrad gespeicherten Energie. Im Bereich stromabwärts des Verdichterrades sind an der integrierten Gehäusewand 10 optional Leitschaufelprofile 25 des Diffusors angeordnet. Die Profile werden beim Abguss des integrierten, inneren Verdichtergehäuses als Kranz vorgesehen und bei der Fertigbearbeitung auf die benötigten Masse gefräst. Auf diese Weise können hohe Lagerhaltungskosten, welche durch die Bewirtschaftung der Diffusoren als separate Teile anfallen eingespart werden, da nicht für jede mögliche Verdichterspezifikationen, also verschiedene Schaufelhöhen oder Profilen, ein nicht austauschbares Teil vorgehalten werden muss. Auch kann durch die Integration der Diffusorprofile 25 in das innere Verdichtergehäuse ein zusätzlicher Pressverband vermieden werden, welcher aufgrund strenger Form- und Lagetoleranzen für die Diffusorhöhe und die Dicke der Diffusorplatte bei der Fertigung mit hohen Produktionskosten verbunden sein kann. Nicht zuletzt lässt sich auch die Anzahl der Bauteile des Verdichters reduzieren. The holding ribs can optionally be equipped with a round, conical or elliptical profile or with a flow profile. The design of the retaining ribs allows the installation of optional sound-absorbing measures in the stabilizer space with little additional constructive auxiliary measures. The overall very soft structure of the integrated inner compressor housing has a positive effect on the behavior in the event of bursting of the compressor wheel. The long housing parts can be easily deformed and absorb a large part of the energy stored in the compressor wheel. In the area downstream of the compressor wheel, guide vanes 25 of the diffuser are optionally arranged on the integrated housing wall 10. The profiles are provided as a ring during casting of the integrated inner compressor housing and milled to the required mass during finishing. In this way, high storage costs, which are incurred by the management of the diffusers as separate parts can be saved because not for each possible compressor specifications, ie different blade heights or profiles, a non-replaceable part must be kept. Also, the integration of the diffuser profiles 25 in the inner compressor housing, an additional press fit can be avoided, which may be due to strict shape and position tolerances for the diffuser height and the thickness of the diffuser plate in the production of high production costs. Last but not least, the number of components of the compressor can be reduced.
Bezugszeichenliste Inneres Verdichtergehäuse mit integrierter Einsatzwand Ringsteg als integrales Bestandteil von 10 Einsatzwand mit Kontur als integrales Bestandteil von 10 Konturnut Eintrittsnut Versteifungsrippe Halterippe für den Ringsteg Äusseres Verdichtergehäuse Diffusorprofil Axiales Sicherungselement Verdichterrad Strömungskanal, Spiralraum Stabilisatorraum List of Reference Numerals Inner compressor housing with integrated insert wall Ring web as an integral part of 10 Insert wall with contour as an integral part of 10 contour groove Entry groove Reinforcing rib Holding rib for the ring land External compressor housing Diffuser profile Axial securing element Compressor wheel Flow channel, spiral space Stabilizer space

Claims

Patentansprüche claims
1. Verdichter, mit im Verdichtergehäuse liegendem, beschaufeltem Verdichterrad, das mit seinem axialen Einlauf im Bereich eines axialen Ansaugkanals liegt, in dem stromauf zum Verdichterrad eine radiale Eintrittsnut (14), stromab zur Eintrittskante des Verdichterrades und im Überdeckungsbereich zu dessen Einlauf eine radiale1. Compressor, lying in the compressor housing, bladed compressor wheel, which lies with its axial inlet in the region of an axial intake passage in the upstream of the compressor a radial inlet groove (14) downstream to the leading edge of the compressor wheel and in the overlap region to the inlet of a radial
Konturnut (13), und die beiden Nuten axial verbindend einen Stabilisatorraum (60) vorgesehen ist, die gegen den Ansaugkanal durch einen Ringsteg (11 ) abgegrenzt ist, wobei der Ringsteg (11 ) einen Teil der Kanalwand bildet und über mehrere Halterippen (16) mit dem inneren 2. Verdichtergehäuse verbunden ist, dadurch gekennzeichnet, dass der Stabilisatorraum (60) zwischen der Eintrittsnut (14) und der Konturnut (13) eine variable Mindesthöhe aufweist.Contour groove (13), and the two grooves axially connecting a stabilizer space (60) is provided, which is delimited against the intake passage by an annular web (11), wherein the annular web (11) forms part of the channel wall and via a plurality of retaining ribs (16) is connected to the inner second compressor housing, characterized in that the stabilizer space (60) between the inlet groove (14) and the contour groove (13) has a variable minimum height.
3. Verdichter nach Anspruch 1 , wobei der Stabilisatorraum (60) zwischen der Eintrittsnut (14) und der Konturnut (13) eine durchschnittliche radiale Mindesthöhe von zwei Dritteln des axialen Abstandes zwischen der Eintrittsnut (14) und der3. The compressor of claim 1, wherein the stabilizer space (60) between the entrance groove (14) and the contour groove (13) has an average radial minimum height of two-thirds of the axial distance between the entrance groove (14) and the
Konturnut (13) aufweist.Contour groove (13).
4. Verdichter nach Anspruch 1 oder 2, wobei das den Stabilisatorraum (60) zum Strömungskanal abgrenzende Verdichtergehäuse (10) einteilig ausgebildet ist.4. The compressor of claim 1 or 2, wherein the stabilizer space (60) delimiting the flow channel compressor housing (10) is integrally formed.
5. Verdichter nach einem der Ansprüche 1 bis 3, wobei das den Stabilisatorraum (60) zum Strömungskanal abgrenzende Verdichtergehäuse mit axial angeordneten5. A compressor according to any one of claims 1 to 3, wherein the stabilizer space (60) delimiting the flow channel compressor housing arranged axially
Versteifungsrippen (15) ausgestattet ist.Stiffening ribs (15) is equipped.
6. Verdichter nach einem der Ansprüche 1 bis 4, wobei das den Stabilisatorraum (60) zum Strömungskanal abgrenzende Verdichtergehäuse zumindest teilweise mit einer thermischen Isolation versehen ist. 6. A compressor according to any one of claims 1 to 4, wherein the stabilizer space (60) delimiting the flow channel compressor housing is at least partially provided with a thermal insulation.
7. Verdichter nach einem der Ansprüche 1 bis 5, wobei zumindest ein Teil der Halterippen (16) von der radialen Richtung abweichend angeordnet ist.7. A compressor according to any one of claims 1 to 5, wherein at least a part of the holding ribs (16) is arranged deviating from the radial direction.
8. Verdichter nach Anspruch 6, wobei die Halterippen (16) zumindest teilweise ungleich von der radialen Richtung abweichend angeordnet sind.8. A compressor according to claim 6, wherein the holding ribs (16) are arranged at least partially different from the radial direction deviating.
9. Verdichter nach einem der Ansprüche 1 bis 7, wobei das den Stabilisatorraum (60) zum Strömungskanal abgrenzende Verdichtergehäuse im Bereich des Strömungskanals stromabwärts des Verdichterrades integrierte Leitschaufeln (25) eines Diffusors umfasst.9. A compressor according to any one of claims 1 to 7, wherein the stabilizer space (60) delimiting the flow channel compressor housing in the region of Flow channel downstream of the compressor wheel integrated vanes (25) comprises a diffuser.
10.Verdichter nach einem der Ansprüche 1 bis 8, wobei der Stabilisatorraums (60) entlang dem Unfang einen sich ändernden Querschnitt aufweist.A compressor according to any one of claims 1 to 8, wherein the stabilizer space (60) has a varying cross-section along the circumference.
11.Verdichter nach einem der Ansprüche 1 bis 9, wobei im Bereich des Stabilisatorraums (60) schalldämmender Mittel vorgesehen sind. 11.Verdichter according to one of claims 1 to 9, wherein in the region of the stabilizer space (60) sound-absorbing means are provided.
PCT/EP2007/058851 2006-08-24 2007-08-24 Compressor housing WO2008023070A1 (en)

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JP2009525082A JP5248501B2 (en) 2006-08-24 2007-08-24 Compressor housing
CN2007800312088A CN101506488B (en) 2006-08-24 2007-08-24 Compressor housing
EP07802892.5A EP2054595B1 (en) 2006-08-24 2007-08-24 Compressor housing

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2722495A1 (en) * 2012-10-17 2014-04-23 ABB Turbo Systems AG Gas entry housing and corresponding exhaust gas turbine
DE102014106415A1 (en) 2014-05-08 2015-11-12 Abb Turbo Systems Ag compressor housing
DE102017114608A1 (en) * 2017-06-30 2019-01-03 Man Diesel & Turbo Se Turbine inlet housing of an axial turbine of a turbocharger
DE102022124126A1 (en) 2022-09-20 2024-03-21 Man Energy Solutions Se Compressor of a turbocharger and turbocharger

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2933459B1 (en) 2012-12-17 2019-02-20 Kawasaki Jukogyo Kabushiki Kaisha Engine supercharger
JP6007815B2 (en) * 2013-02-12 2016-10-12 トヨタ自動車株式会社 Turbocharger
CN109394018A (en) * 2017-08-18 2019-03-01 美的集团股份有限公司 Base assembly and cooking machine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4213047A1 (en) * 1992-04-21 1993-10-28 Kuehnle Kopp Kausch Ag Radial compressor for vehicle exhaust gas turbocharger - uses feed pipe to deliver flow medium to influence conditions in circulation chamber
GB2319304A (en) * 1996-11-18 1998-05-20 Daimler Benz Ag Exhaust-gas turbocharger
US20020071765A1 (en) * 2000-12-13 2002-06-13 Sahay Sunil Nandan Turbocharger noise deflector
EP1473463A1 (en) * 2003-04-30 2004-11-03 Holset Engineering Co. Limited Compressor
US20040223843A1 (en) * 2003-05-05 2004-11-11 Jose Cabrales Apparatus, system and method for minimizing resonant forces in a compressor

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3978974B2 (en) * 2000-04-03 2007-09-19 株式会社豊田自動織機 Piston in compressor and piston manufacturing method

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4213047A1 (en) * 1992-04-21 1993-10-28 Kuehnle Kopp Kausch Ag Radial compressor for vehicle exhaust gas turbocharger - uses feed pipe to deliver flow medium to influence conditions in circulation chamber
GB2319304A (en) * 1996-11-18 1998-05-20 Daimler Benz Ag Exhaust-gas turbocharger
US20020071765A1 (en) * 2000-12-13 2002-06-13 Sahay Sunil Nandan Turbocharger noise deflector
EP1473463A1 (en) * 2003-04-30 2004-11-03 Holset Engineering Co. Limited Compressor
US20040223843A1 (en) * 2003-05-05 2004-11-11 Jose Cabrales Apparatus, system and method for minimizing resonant forces in a compressor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2722495A1 (en) * 2012-10-17 2014-04-23 ABB Turbo Systems AG Gas entry housing and corresponding exhaust gas turbine
KR101536056B1 (en) * 2012-10-17 2015-07-10 에이비비 터보 시스템즈 아게 Gas inlet housing
DE102014106415A1 (en) 2014-05-08 2015-11-12 Abb Turbo Systems Ag compressor housing
WO2015169509A1 (en) * 2014-05-08 2015-11-12 Abb Turbo Systems Ag Compressor housing
DE102017114608A1 (en) * 2017-06-30 2019-01-03 Man Diesel & Turbo Se Turbine inlet housing of an axial turbine of a turbocharger
DE102022124126A1 (en) 2022-09-20 2024-03-21 Man Energy Solutions Se Compressor of a turbocharger and turbocharger

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KR20090035601A (en) 2009-04-09
EP2054595A1 (en) 2009-05-06
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CN101506488A (en) 2009-08-12
EP2054595B1 (en) 2015-02-25
JP5248501B2 (en) 2013-07-31

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